Drag Coefficient Model Using the Cercignani–Lampis–Lord Gas–Surface Interaction Model

Walker, Andrew; Mehta, Piyush M.; Koller, J.

doi:10.2514/1.a32677

Cited by 55 publications

(67 citation statements)

References 38 publications

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“…Pilinski et al [] use the fractional coverage to compute the effective energy accommodation, coefficient α eff , as

α_{eff} = (1 - θ) α_{s} + θ α_{ads}

where α s is the accommodation coefficient based on a clean satellite surface and α ads is the accommodation coefficient based on a satellite surface completely covered with an adsorbate (atomic oxygen). Here we use the more recently developed model of Walker et al [] that modifies the work of Pilinski et al [] by using the fractional coverage to compute the total

{scriptC}_{D}

{scriptC}_{D, T} = (1 - θ) {scriptC}_{D, s} + θ {scriptC}_{D, ads}

where

{scriptC}_{D, s}

is the drag coefficient based on a clean satellite surface and

{scriptC}_{D, ads}

is the drag coefficient based on a satellite surface completely covered with an adsorbate (atomic oxygen).…”

Section: Accelerometer‐derived Densitiesmentioning

confidence: 99%

“…We use the model of Walker et al [] because particles will interact either with the clean surface or adsorbate‐covered surface. Therefore, a total weighted

{scriptC}_{D}

is more realistic and physical than the notion of an effective accommodation coefficient.…”

Section: Accelerometer‐derived Densitiesmentioning

confidence: 99%

“…Computing physical

{scriptC}_{D}

requires, among other things, accurate knowledge of the mole fractions of atmospheric constituents and the energy and momentum accommodation coefficients [ Mehta et al , ]. The sensitivity of physical satellite

{scriptC}_{D}

to atmospheric constituents and energy accommodation has been studied in detail and shows a strong dependence of up to 20% for GRACE and other satellites [ Mehta et al , ; Walker et al , ].…”

Section: Introductionmentioning

confidence: 99%

See 2 more Smart Citations

New density estimates derived using accelerometers on board the CHAMP and GRACE satellites

et al. 2017

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Atmospheric mass density estimates derived from accelerometers onboard satellites such as CHAllenging Minisatellite Payload (CHAMP) and Gravity Recovery and Climate Experiment (GRACE) are crucial in gaining insight into open science questions about the dynamic coupling between space weather events and the upper atmosphere. Recent advances in physics‐based satellite drag coefficient modeling allow derivation of new density data sets. This paper uses physics‐based satellite drag coefficient models for CHAMP and GRACE to derive new estimates for the neutral atmospheric density. Results show an average difference of 14–18% for CHAMP and 10–24% for GRACE between the new and existing data sets depending on the space weather conditions (i.e., solar and geomagnetic activity levels). The newly derived densities are also compared with existing models, and results are presented. These densities are expected to be useful to the wider scientific community for validating the development of physics‐based models and helping to answer open scientific questions regarding our understanding of upper atmosphere dynamics such as the sensitivity of temporal and global density variations to solar and geomagnetic forcing.

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“…Pilinski et al [] use the fractional coverage to compute the effective energy accommodation, coefficient α eff , as

α_{eff} = (1 - θ) α_{s} + θ α_{ads}

{scriptC}_{D}

{scriptC}_{D, T} = (1 - θ) {scriptC}_{D, s} + θ {scriptC}_{D, ads}

where

{scriptC}_{D, s}

is the drag coefficient based on a clean satellite surface and

{scriptC}_{D, ads}

is the drag coefficient based on a satellite surface completely covered with an adsorbate (atomic oxygen).…”

Section: Accelerometer‐derived Densitiesmentioning

confidence: 99%

“…We use the model of Walker et al [] because particles will interact either with the clean surface or adsorbate‐covered surface. Therefore, a total weighted

{scriptC}_{D}

is more realistic and physical than the notion of an effective accommodation coefficient.…”

Section: Accelerometer‐derived Densitiesmentioning

confidence: 99%

“…Computing physical

{scriptC}_{D}

{scriptC}_{D}

to atmospheric constituents and energy accommodation has been studied in detail and shows a strong dependence of up to 20% for GRACE and other satellites [ Mehta et al , ; Walker et al , ].…”

Section: Introductionmentioning

confidence: 99%

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New density estimates derived using accelerometers on board the CHAMP and GRACE satellites

et al. 2017

View full text Add to dashboard Cite

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“…For no significant additional cost, the CLL model gave more realistic scattering distributions [11]. CLL model is widely recognized examples of its application are presented in multiple works [11][12][13][14][15][16][17][18][19][20][21][22][23][24][25][26][27][28].…”

Section: The Description Of Gas-surface Interaction Modelsmentioning

confidence: 99%

Effects of Gas-surface Interaction Models on Spacecraft Aerodynamics

Khlopkov¹,

Chernyshev²,

Myint³

et al. 2016

International Journal of Aeronautical and Space Sciences

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The influence of boundary condition of the bodies with gas flows is one of the most important problems in high-altitude aerodynamics. In this paper presents the results of the calculation of aerodynamic characteristics of aerospace vehicle using Monte-Carlo method based on three different gas-surface interaction models -Maxwell model, Cercignani-Lampis-Lord (CLL) model and Lennard-Jones (LJ) potential. These models are very sensitive for force and moment coefficients of aerospace vehicle in the hypersonic free molecular flow. The models, method and results can be used for new generation aerospace vehicle design.

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“…7 for high solar activity). Below 150 km, the collisions between particles start to be important, and the accuracy of analytical FMF solutions decreases [41]. The quantification of this effect requires the use of computationally intensive numerical codes, like direct simulation Monte Carlo [42].…”

Section: Environmental Torquesmentioning

confidence: 99%

Perigee Attitude Maneuvers of Geostationary Satellites During Electric Orbit Raising

Prieto

Roberts

2017

Journal of Guidance, Control, and Dynamics

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When full-electric orbit-raising trajectories begin in a classic geostationary transfer orbit with low initial perigee altitude, the need for deployed solar arrays to power the propulsion system significantly increases the aerodynamic and gravity gradient torques. In fact, the torque magnitudes in the first few perigee passages may become a challenging requirement for the attitude control system. Apart from oversizing actuators, other solutions may include the need for a backup thruster system or raising the perigee altitude, implying mass penalties and cost. This paper presents the design of an optimal attitude maneuver at the perigee that can be undertaken using nominal reaction wheels. Attitude paths avoiding saturation of the wheels while dumping accumulated momentum are obtained performing a physically consistent modeling of aerodynamic torques and using pseudospectral methods to solve the trajectory optimization problem. The optimization of solar array positions is also explored to further constrain the problem or improve the maneuver performance. Resulting mass and cost savings can be significant, which could be used for additional payload or to significantly extend the operational life of the satellite.

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Drag Coefficient Model Using the Cercignani–Lampis–Lord Gas–Surface Interaction Model

Cited by 55 publications

References 38 publications

New density estimates derived using accelerometers on board the CHAMP and GRACE satellites

New density estimates derived using accelerometers on board the CHAMP and GRACE satellites

Effects of Gas-surface Interaction Models on Spacecraft Aerodynamics

Perigee Attitude Maneuvers of Geostationary Satellites During Electric Orbit Raising

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